Results
2023-17-01: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a determination that some batches of nose landing gear (NLG) drag brace panels (DBP) having certain part numbers were affected by a quality deficiency that was not detected in production. This AD requires a measurement of the affected part and, depending on findings, accomplishment of applicable corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
97-06-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires inspections to detect cracking on the free edge of the tang, if necessary, and of the fastener holes in the lower spar chord; and various follow-on actions. This action also provides for optional terminating action for the requirements of this AD. This amendment is prompted by a report of fatigue cracking in the lower spar chord of two Model 757 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced structural integrity of the engine strut.
2005-03-16: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model DH.125, HS.125, and BH.125 series airplanes; BAe.125 series 800A (C-29A and U-125) and 800B airplanes; and Hawker 800 (including variant U-125A) and 800XP airplanes. This AD requires installing insulating blankets on the engine compartment firewall and the wire harness passing through the firewall fairlead. This AD is prompted by a report indicating that insulation on the wire harness passing through the firewall fairlead ignited on the fuselage side of the firewall. We are issuing this AD to prevent a fire in the engine compartment from causing possible ignition of outgassing wire insulation on the fuselage side of the firewall, which could lead to an uncontrollable fire in the fuselage.
2023-17-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements, produced before January 31, 2021, may not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires a one-time special detailed inspection (SDI) for discrepancies of each affected part installed at an affected position, and replacement of discrepant parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD would also prohibit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
93-22-01: 93-22-01 FOKKER: Amendment 39-8726. Docket 93-NM-84-AD. Applicability: Model F28 Mk 0100 series airplanes, serial numbers 11244 through 11392 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inadvertent positive voltage on the wiring of the liftdumper system, accomplish the following: (a) Within 8 months after the effective date of this AD, inspect the liftdumper system wiring shield ground connections to determine if the shields are connected to ground, in accordance with Fokker Service Bulletin SBF100-27-043, dated October 1, 1992. If any shield is not connected to ground, prior to further flight, connect the shield to ground in accordance with the service bulletin. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection and connection shall be done in accordance with Fokker Service Bulletin SBF100-27-043, dated October 1, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 16, 1993.
2023-17-51: The FAA is adopting a new airworthiness directive (AD) for all Bell Textron Canada Limited Model 407 helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of a disbonded area in a tail rotor (T/R) blade. This AD requires determining if an affected T/R blade is installed, inspecting each of those T/R blades and, depending on the results, replacing the T/R blade as specified in a Transport Canada emergency AD, which is incorporated by reference. This AD also limits the installation of T/R blades to certain T/R blades. The FAA is issuing this AD to address the unsafe condition on these products.
2005-03-06: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland Ltd. & Co KG (RRD) (formerly Rolls- Royce plc) Model Tay 611-8, 620-15, 650-15, and 651-54 turbofan engines, with low pressure (LP) fuel tube, part number (P/N) JR33021A, installed. That AD currently requires initial and repetitive inspections of the LP fuel tubes. This AD requires the same inspections and adds a requirement to replace the fuel tube with a new design tube, as mandatory terminating action to the repetitive inspections. This AD results from the manufacturer introducing a new design fuel tube, which eliminates the unsafe condition. We are issuing this AD to prevent a dual-engine flameout due to fuel exhaustion, which could lead to forced landing and possible damage to the airplane.
2023-17-09: The FAA is superseding Airworthiness Directive (AD) 2022-13- 03, which applied to a certain Cameron Balloons Ltd. (Cameron) fuel cylinder installed on hot air balloons. AD 2022-13-03 required removing any installed fuel cylinder part number (P/N) CB2990 (Alugas) from service before further flight. Since the FAA issued AD 2022-13-03, the fuel cylinder part number has been identified as CB2990/A instead of CB2990 (Alugas). This AD requires removing any installed fuel cylinders P/N CB2990/A from service before further flight. The FAA is issuing this AD to address the unsafe condition on these products.
2000-17-02: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and certain Model Avro 146-RJ series airplanes, that requires inspections and torque checks of the stringer crown fittings and bolts at Ribs 0 and 2 of the wings for discrepancies, corrective action, if necessary; and eventual modification of the stringer crown fittings, which terminates the inspections and checks. This amendment is necessary to prevent increased loads on the upper wing skin due to looseness of the stringer fittings and bolts at Ribs 0 and 2 of the wings, which could result in reduced structural integrity of the wings. This action is intended to address the identified unsafe condition.
2000-17-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently requires a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, if necessary. This amendment requires new inspections (one-time detailed visual inspection and repetitive eddy current or dye penetrant inspections) to detect cracking of the NLG main fitting subassembly, and corrective actions, if necessary. This amendment also revises the applicability of the existing AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flightcrew and passengers.
2012-17-09: We are adopting a new airworthiness directive (AD) for Eurocopter France Model SA341G helicopters. This AD requires replacing any rotating star with more than 12,000 hours TIS. This AD was prompted by an analysis and tests performed by the manufacturer that indicate that the life limit of the rotating star should be 12,000 hours time- in-service (TIS). The actions of this AD are intended to prevent failure of the rotating star and subsequent loss of control of the helicopter.
2023-16-07: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, LLC (IAE LLC) Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM, PW1127GA-JM, PW1129G- JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines. This AD was prompted by an updated analysis of an event involving an IAE LLC Model PW1127GA-JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an aborted takeoff. This AD requires performing an ultrasonic inspection (USI) of the high-pressure turbine (HPT) 1st- stage hub and HPT 2nd-stage hub for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hub or HPT 2nd- stage hub. The FAA is issuing this AD to address the unsafe condition on these products.
2000-17-08: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Deutschland GMBH (ECD) Model BO-105A, BO-105C, BO-105 C-2, BO-105 CB-2, BO-105 CB-4, BO-105S, BO-105 CS-2, BO-105 CBS-2, BO-105 CBS-4, and BO-105LS A-1 helicopters. That AD requires creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap. That AD also requires inspecting and removing, as necessary, certain unairworthy TT straps. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by a need to establish a life limit for certain TT straps because of an accident in which a main rotor blade (blade) separated from an ECD Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the ECD Model BO-105 helicopters. The actions specified by this AD are intended to prevent fatigue failure of the TT strap, loss of a blade, and subsequent loss of control of the helicopter.
2000-17-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires repetitive inspections to detect discrepancies in the upper and lower skins of the fuselage lap joint, and repair, if necessary. This action is necessary to detect and correct such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid decompression of the airplane fuselage.
2012-15-13: We are superseding an existing airworthiness directive (AD) for all Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The existing AD currently requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220; and related investigative and corrective actions if necessary. That AD requires modifying the frame-to-tension-tie joints at body stations 1120 through 1220 (including related investigative actions and corrective actions if necessary), which provides a terminating action for the repetitive inspections. That AD also requires new repetitive inspections after the modification, corrective actions if necessary, and additional modification requirements at a specified time after the first modification. That AD also removed certain airplanes from the applicability. That AD was prompted by reports of cracked and severed tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. This AD revises the existing AD by adding repetitive open hole high frequency eddy current (HFEC) inspections for cracking in the forward and aft tension tie channels, and repair if necessary. For certain airplanes, this AD also requires a one-time angle inspection to determine if the angle is installed correctly, and re-installation if necessary; and a one-time open hole HFEC inspection at the fastener locations where the tension tie previously attached to the frame prior to certain modifications, and repair if necessary. This AD also, for the Stage 2 inspections, reduces the initial compliance times for those inspections. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression and reduced structural integrity of the airplane.
2023-16-05: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of the main landing gear (MLG) aft door not opening when using the alternate extension system. This AD requires a one-time inspection of the spring box assembly, repetitive inspections of the cam assembly and alternate release cable assembly, corrective actions if necessary, and a replacement of certain alternate release cable assemblies. In addition, this AD requires certain aircraft maintenance manuals tasks when installing the cam assembly or alternate release cable assembly. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
78-20-08: 78-20-08 BEECH: Amendment 39-3311. Applies to Model 76 (Serial Numbers ME-1 through ME-62 and ME-66) airplanes. To preclude failure of the rudder and elevator trim tab push rods, prior to further flight: A) If not previously accomplished, replace Beech Part Number 105-520024-5 rudder trim tab push rod with new Beech Part Number 105-520045-9 rudder trim tab push rod and rebalance the rudder control surface, where necessary, in accordance with Beechcraft Liberal Service Letter No. 78-4 dated September 14, 1978, or later approved revisions. B) If not previously accomplished, replace Beech Part Number 105-520024-1 elevator trim tab push rod with new Beech Part Number 105-520048-1 elevator trim tab push rod and rebalance the elevator control surfaces, where necessary, in accordance with Beechcraft Liberal Service Letter No. 78-4 dated September 14, 1978, or later approved revisions. C) Aircraft may not be flown in accordance with FAR 21.197 to a base to accomplish this AD, unless authorized by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 12, 1978, to all persons except those to whom it has already been made effective by telegram from the FAA dated September 9, 1978.
2000-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes, and Model MD-10-10F and MD-10-30F series airplanes that requires performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This AD also requires replacing all bolts with bolts made from Inconel, which constitutes terminating action for the repetitive inspection requirements. This amendment is prompted by an in-flight loss of the inboard flap assembly on an airplane during approach for landing. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure of H-11 attaching bolts, which could result in reduced controllability of the airplane.
2005-03-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (Bell) Model 407 helicopters that requires creating a component history card or equivalent record for each crosstube assembly, converting accumulated run-on landings to an accumulated Retirement Index Number (RIN) count, and establishing a maximum accumulated RIN for certain crosstube assemblies. This amendment is prompted by fatigue testing, analysis, and evaluation by the manufacturer that determined that run-on landings impose a high stress on landing gear or crosstubes and may cause cracking in the area above the skid tube saddle. The actions specified by this AD are intended to prevent fatigue failure in a crosstube assembly due to excessive stress during run-on landings and subsequent loss of control of the helicopter.
2023-08-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-201, -202, -203, -301, -302, and -303 airplanes. This AD was prompted by reports of corrosion and cracks found on engine inlet attach fittings. This AD requires an inspection to determine whether affected engine inlet attach fittings are installed, and replacement of those affected engine inlet attach fittings or replacement with and inlet cowl having no affected engine inlet attach fittings, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
96-04-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This amendment requires repetitive inspections to detect distortion and/or cracks on the attachment brackets of the backrest recline control locks of certain seats. It also provides for an optional modification which, if accomplished, terminates the repetitive inspections. This amendment is prompted by a report of failure of the bracket of the backrest recline control lock on a seat due to fatigue-related cracking. The actions specified by this AD are intended to prevent fatigue-related cracking and/or distortion, which could result in failure of the seat backrest attach fitting, and the subsequent uncommanded 50 angle recline of the pilot or co-pilot seat; this situation could lead to the temporary inability of the pilots to control the airplane.
2000-16-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive inspections to check for backlash of the spherical bearing of the active aileron servo-controls, and follow-on corrective actions, if necessary. This amendment also provides optional terminating action for the repetitive inspections. This action is necessary to detect and correct excess backlash of the spherical bearing of the active aileron servo-controls, which could result in failure of the active aileron servo-controls and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2005-03-05: The FAA is revising an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model MD-90-30 airplanes. This AD requires a one-time general visual inspection to detect wire chafing damage and to determine adequate clearance between the disconnect panel structure and the wires above the aft left lavatory; and corrective actions, if necessary. This new AD revises the applicability of the existing AD. This AD is prompted by the determination that certain airplanes unaffected by the existing AD are subject to the unsafe condition, and certain other airplanes should be removed from the applicability. We are issuing this AD to prevent damage to certain wires due to contact between the wires and the adjacent structure, which could result in electrical arcing and consequent smoke and fire in the cabin.
91-03-01: 91-03-01 BOEING HELICOPTERS (BOEING VERTOL HELICOPTER CO.): Amendment 39-6862. Docket No. 90-ASW-47-AD. Applicability: All Model 234 series helicopter, with serial numbers (S/N) MJ001, MJ002, MJ003, MJ005, MJ006, MJ016, MJ017, MJ022, MJ023, MM819, MM820, and MM821, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of a rotor blade damper elastomeric rod end, which could result in the rotor blade striking the helicopter during start up or shut down, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD inspect all rod ends, part number (P/N) 234RS202-1 and -2, with more than 350 hours' time in service, unless accomplished within the last 40 hours' time in service. Thereafter, inspect these rod ends at intervals not to exceed 25 hours' time in service from the last inspection. Conduct these inspections using eddy current inspection methodsapproved by the FAA. NOTE: The Accomplishment Instructions of paragraphs 3.B and C of Boeing Helicopters Service Bulletin 234-62-1031, dated September 26, 1990, provide an FAA approved calibration and inspection procedure for eddy current inspection of the rod ends. (b) Conduct an FAA approved eddy current inspection of any used spare serviceable rod end, P/N 234RS202-1 or -2, with more than 350 hours' time in service prior to installation and return to service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. (c) If a crack is found, replace the cracked rod end with a serviceable rod end prior to further flight. (d) Helicopters may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished. (e) Alternate inspections, modification, other actions, or adjustment of the compliance times, which provides an equivalent level of safety maybe used when approved by the Manager, New York Aircraft Certification Office, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6862, AD 91-03-01) becomes effective on February 14, 1991.
2000-16-02: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series turbofan engines. The current AD requires initial and repetitive torque checks for loose or broken bolts used to secure the engine to the airplane made from INCO 718 material (front pylon mount bolts). The current AD also requires the replacement of the bolts, if necessary, with new bolts, and establishes a new cyclic life limit for the front pylon mount bolt. This amendment adds requirements for initial and repetitive torque checks of front pylon mount bolts made from a new material, MP159, and initial and repetitive visual inspections of the primary mount thrust load path. This amendment is prompted by the use of front pylon mount bolts made from MP159 material and fatigue testing that shows that the forward engine mount bearing housings have insufficient fatigue life expectancy. The actions specified by this AD are intended to prevent frontpylon mount bolt and primary mount thrust load path failure, which could result in an engine separating from the airplane.